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        <identifier>oai:www.ideals.illinois.edu:2142/85124</identifier>
        <datestamp>2023-07-11</datestamp>
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        <thesis xmlns="http://www.ndltd.org/standards/metadata/etdms/1.1/" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns:dc="http://purl.org/dc/elements/1.1/" xsi:schemaLocation="http://www.ndltd.org/standards/metadata/etdms/1.1/ http://www.ndltd.org/standards/metadata/etdms/1.1/etdms11.xsd http://purl.org/dc/elements/1.1/ http://www.ndltd.org/standards/metadata/etdms/1.1/etdmsdc.xsd">
          <dc:contributor>Prussing, John E.</dc:contributor>
          <dc:creator>Jo, Jang-Won</dc:creator>
          <dc:date>2015-09-25T22:34:30Z</dc:date>
          <dc:date>2015-09-25T22:34:30Z</dc:date>
          <dc:date>10000-01-01</dc:date>
          <dc:date>1997</dc:date>
          <dc:date>1997</dc:date>
          <dc:description>"A recent advance in sufficient conditions for a weak local minimum in optimal control problems is used to develop a procedure for applying second-order necessary and sufficient conditions for a minimum of a cost functional. For a system with n state variables, an improved Riccati equation solution method is used to transform a test for the unboundedness of a n x n matrix into a test for a scalar being zero. Application to one important second-order necessary and sufficient condition, the Jacobi no-conjugate-point condition, is introduced using the ""Shortest path between two points on a sphere"" problem. Second-order necessary and sufficient conditions are applied to various optimal control problems, including spacecraft trajectory problems with constant thrust acceleration and with time-varying low thrust acceleration for a power-limited rocket engine. A solution that simultaneously maximizes final orbit energy and minimizes propellant consumption is found that satisfies the usual first-order necessary conditions, but is non-optimal. Other example variational problems are investigated: Hamilton's Principle for several dynamic systems, including a circular orbit in an inverse-square gravitational field and projectile motion in a uniform field, as well as a simple example of Zermelo's problem. For those solutions that satisfy first-order necessary conditions but are non-optimal, a Genetic Algorithm is successfully used to find a global near-optimal solution of lower cost."</dc:description>
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  Previous issue date: 1997</dc:description>
          <dc:description>Embargo set by: Seth Robbins for item 86405
Lift date: Forever
Reason: Restricted to the U of I community idenfinitely during batch ingest of legacy ETDs</dc:description>
          <dc:description>Restricted to the U of I community idenfinitely during batch ingest of legacy ETDs</dc:description>
          <dc:description>U of I Only</dc:description>
          <dc:description>157 p.</dc:description>
          <dc:description>Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 1997.</dc:description>
          <dc:identifier>http://hdl.handle.net/2142/85124</dc:identifier>
          <dc:identifier>(MiAaPQ)AAI9737146</dc:identifier>
          <dc:language>eng</dc:language>
          <dc:subject>Operations Research</dc:subject>
          <dc:title>Applications of Second-Order Necessary and Sufficient Conditions to Optimal Trajectories</dc:title>
          <dc:type>text</dc:type>
          <degree>
            <department>Aerospace Engineering</department>
            <discipline>Aerospace Engineering</discipline>
            <grantor>University of Illinois at Urbana-Champaign</grantor>
            <level>Dissertation</level>
            <name>Ph.D.</name>
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